EP3510255B1 - Method for clear position determination and identification of a turbine blade - Google Patents
Method for clear position determination and identification of a turbine blade Download PDFInfo
- Publication number
- EP3510255B1 EP3510255B1 EP17768699.5A EP17768699A EP3510255B1 EP 3510255 B1 EP3510255 B1 EP 3510255B1 EP 17768699 A EP17768699 A EP 17768699A EP 3510255 B1 EP3510255 B1 EP 3510255B1
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- European Patent Office
- Prior art keywords
- turbine
- blade
- boroscope
- blade lock
- gas turbine
- Prior art date
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- 238000000034 method Methods 0.000 title claims description 19
- 238000001514 detection method Methods 0.000 claims 1
- 208000012886 Vertigo Diseases 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000018109 developmental process Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 230000003287 optical effect Effects 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
Images
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
- F01D25/285—Temporary support structures, e.g. for testing, assembling, installing, repairing; Assembly methods using such structures
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/005—Repairing methods or devices
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/72—Maintenance
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/80—Diagnostics
Definitions
- the invention relates to a method for the unambiguous position assignment and identification of a turbine blade of a high-pressure turbine stage of a gas turbine, in particular of an aircraft engine.
- the turbine blades of the high pressure turbine are among the most stressed components of a gas turbine or an aircraft engine. At the same time, even small damage or deviations from their respective original shape of the high-pressure turbine turbine blades have a not inconsiderable influence on the efficiency of the gas turbine, which ultimately has an effect on fuel consumption.
- the high-pressure turbine blades are regularly overhauled or, if this is not possible, replaced with new parts.
- the gas turbine must be dismantled at least to such an extent that the turbine blades of the high-pressure turbine can be removed.
- the previously removed turbine blades can be reassembled after a possibly time-consuming overhaul.
- other turbine blades or new parts that have already been otherwise overhauled can be installed in order to keep the required maintenance time for the gas turbine as short as possible. The latter is particularly important in aircraft engines.
- Turbine blades regularly have a unique serial number. For turbine blades of aircraft engines is this is even mandatory due to approval regulations.
- the serial numbers are arranged on the base of the turbine blades, with which the blades are attached to the blade carrier of the engine, in order to avoid that they come into direct contact with the hot gas flow and are made unrecognizable by it.
- serial number at the base of a turbine blade
- the serial numbers can no longer be viewed after the turbine blades have been inserted.
- the documents DE 10 2011 103 003 A1 and US 9 016 560 B2 disclose automated optical methods for checking dismantled engine blades, wherein the serial number provided on the blade root can be designed to be machine-readable.
- Gas turbine and aircraft engine blades include an airfoil and a root.
- the blade root regularly has a shape that enables the blade root to be pushed into a blade groove of the blade carrier of a turbine stage.
- blade locks are provided with which the blades are fixed in their position relative to the blade carrier.
- the invention is based on the knowledge that the areas of the high-pressure turbine that can be seen through a second borescope in a fully assembled gas turbine are subject to the particular load caused by the hot gas coming from the combustion chamber, which is why all markings made in this area are removed or removed at the latest with a first test run of the gas turbine would be burned. Due to the particular load in this area, the high-pressure turbines are also regularly designed in such a way that the surfaces of the high-pressure turbine, which can be viewed through a second borescope when the gas turbine is fully assembled, cannot draw any conclusions about their angular position or the like. allow.
- the invention has recognized that the high-pressure compressor, which is non-rotatably connected to the high-pressure turbine via a shaft, has clearly identifiable vane locks through a first borescope, even when the gas turbine is fully installed, which can serve as an identification feature for the angular position of the high-pressure compressor and thus the high-pressure turbine.
- the position of the borescope openings for the first and second borescopes it is possible to determine precisely which turbine blade is in the field of view of the second boroscope when the specified blade lock is in the field of view of the first boroscope.
- a first turbine blade can initially be clearly identified on the basis of this information on the record card when the gas turbine is fully assembled.
- the other turbine blades can also be clearly identified using the relative position of the turbine blades recorded on the record map.
- the angular position of the specified blade lock of the high pressure compressor relative to the shaft is marked on the shaft itself and, based on this marking, the turbine blade to be marked on the record card is determined.
- the marking can be brought up to the high pressure turbine along the shaft, which simplifies the identification of the turbine blade in question.
- the marking can be carried out, for example, using a marking pen in accordance with the DIN LN 9051 standard.
- the determination of the turbine blades to be marked on the record card can alternatively or additionally be made easier if the turbine blades have a temporary identification feature that is visible after assembly.
- a temporary identification feature that is visible after assembly.
- the serial number of the individual turbine blades must be applied directly to the blade, i.e. at a point that is also visible after the turbine blade has been installed.
- Such an identification feature which is also visible in the installed state, is basically a temporary identification feature which, after a first test run of the gas turbine, has already been burned without residue due to the particular loads in the area of the high-pressure turbine.
- a first and a second vane lock can usually be clearly identified.
- the distance in the circumferential direction opposite to a predetermined direction of rotation between the first shovel lock and the second shovel lock is usually less than the corresponding distance between the last shovel lock - which can also be the second shovel lock - and the first Shovel lock.
- the second shovel lock is the shovel lock following the first shovel lock in the specified direction of rotation in the circumferential direction. It is preferred if the specified shovel lock is the second shovel lock. As explained below, this can facilitate the later identification of the turbine marked on the record card.
- a first borescope is guided through a first borescope opening on the gas turbine and a second borescope is guided through a second borescope opening on the gas turbine.
- the first borescope opening is arranged so that the given blade lock of the given stage of the high pressure compressor can be seen through a passed borescope, while the second borescope opening allows the turbine blades of the relevant high pressure turbine stage to be viewed with the aid of a boroscope.
- the second borescope After introducing at least the first boroscope - the second borescope can also be inserted later - the shaft is turned on both the high pressure compressor and the high pressure turbine stage until the specified blade lock is in the field of view of the first boroscope.
- the turbine blade which is then visible through the second borescope, which has now been introduced at the latest, is then the turbine blade marked on the record card.
- the rotational speed can be determined after the first shovel lock can preferably be reduced by the first borescope in order to be able to stop the wave without delay as soon as the second shovel lock is in the field of view of the first borescope.
- the rotational speed can initially be comparatively high in order to quickly turn the shaft into the area in which the second shovel lock is located, in order then to be able to stop the shaft immediately due to a comparatively low rotational speed as soon as the second shovel lock is in the field of vision of the first Boroscope is coming.
- At least one turbine blade can be identified on the basis of the rate card, preferably by subsequently turning the shaft connecting the high pressure compressor and the high pressure turbine stage while observing the turbine blades through the second borescope or while observing the change in the angular position of the shaft. Since the relative position of the individual turbine blades can be seen on the record card, starting from the clearly identified, marked turbine blade, the respective adjacent turbine blades and successively the adjacent turbine blades can be identified. Since the basic geometric configuration of the turbine blades of a gas turbine is known, a turbine blade that is not adjacent to the highlighted turbine blade can also be identified directly via the angular position of the shaft, starting from the angular position that the shaft assumes when the marked turbine blade is identified.
- Figure 1 is a schematic representation of a high pressure turbine stage 10 of a gas turbine 1 or an aircraft engine 1 (see Figure 3 ).
- the high-pressure turbine stage 10 has a multiplicity of turbine blades 11, the respective serial numbers of which are engraved on the blade root and their relative position is recorded on a record card.
- a record card can have the form of a list of serial numbers, the order of the listing corresponding to the arrangement of the turbine blades in the circumferential direction of the high-pressure turbine stage.
- the high-pressure turbine stage 10 is non-rotatably connected to a two-stage high-pressure compressor 30 via a shaft 20.
- Each of the two stages of the high-pressure compressor 30 comprises a plurality of compressor blades 31, which are each connected via two blade locks 32 (in the illustration according to FIG Figure 1 only a blade lock 32 is visible) are secured in their position relative to the blade carrier of the respective stage of the high-pressure compressor 30.
- FIG 2 the high pressure compressor 30 is off Figure 1 shown enlarged.
- Two blade locks 32, 32 ' can be seen between the blades 31 of the one stage of the high-pressure compressor 30.
- the distance in the circumferential direction between the first shovel lock 32 'and the second shovel lock 32 is opposite to the predetermined direction of rotation 90 - the does not have to coincide with the direction of rotation of the aircraft engine 1 during operation - less than the distance between the second and last blade lock 32 in the direction of rotation and the first blade lock 32 '.
- the shovel lock 32 identified in this way as the second shovel lock 32 serves as the basis for the marking 21 along the shaft 20, which is applied with an aviation-certified marking pen.
- the marking 21 indicates the angular position of the shovel lock 32 relative to the axis of the shaft 20.
- that turbine blade 11 'can be marked on the record card which - as below with the aid of Figure 3 is explained - in the fully assembled state of the aircraft engine 1 in the field of view of a second borescope 42 guided through a second borescope opening 5 on the aircraft engine 1, when the specified blade lock 32 is in the field of view of a first borescope 41 guided through a first borescope opening 4 of the aircraft engine 1.
- the shaft 20 is rotated in the direction of rotation 90 at a first rotational speed.
- the rotational speed is reduced and the shaft 20 is stopped as soon as the second shovel lock 32 is in the field of view of the first borescope 41.
- the turbine blade 11 marked on the record card is directly in the field of view of the second boroscope 42 due to the previously carried out position assignment of the turbine blade 11 in question 'can be clearly identified using the rate card.
- any markings provided on the turbine blades 11 during assembly which can also facilitate the assignment of the position of the turbine blade 11 'to be marked, are completely removed after the first test run of the aircraft engine 1 at the latest.
- the method according to the invention makes it possible to first identify a turbine blade 11 '- namely the one previously marked on the record card - without any identification features on the turbine blade 11' or the high-pressure turbine 10 itself. Starting from this turbine blade 11 ', the other turbine blades 11 can also be clearly identified with the aid of the record card.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
Die Erfindung betrifft Verfahren zur eindeutigen Positionszuordnung und Identifizierung einer Turbinenschaufel einer Hochdruckturbinenstufe einer Gasturbine, insbesondere eines Flugzeugtriebwerks.The invention relates to a method for the unambiguous position assignment and identification of a turbine blade of a high-pressure turbine stage of a gas turbine, in particular of an aircraft engine.
Die Turbinenschaufeln der Hochdruckturbine gehören zu den am meisten beanspruchten Bauteilen einer Gasturbine bzw. eines Flugzeugtriebwerks. Gleichzeitig haben bereits kleine Beschädigungen oder Abweichungen von ihrer jeweiligen Ursprungsform der Hochdruckturbinenturbinenschaufeln nicht unerheblichen Einfluss auf den Wirkungsgrad der Gasturbine, was sich letztendlich auf den Treibstoffverbrauch auswirkt.The turbine blades of the high pressure turbine are among the most stressed components of a gas turbine or an aircraft engine. At the same time, even small damage or deviations from their respective original shape of the high-pressure turbine turbine blades have a not inconsiderable influence on the efficiency of the gas turbine, which ultimately has an effect on fuel consumption.
Aufgrund der besonderen Belastung werden die Hochdruckturbinenschaufeln regelmäßig überholt oder, sofern dies nicht möglich ist, durch Neuteile ersetzt. Dazu muss die Gasturbine zumindest soweit zerlegt werden, dass die Turbinenschaufeln der Hochdruckturbine abmontiert werden können. Die zuvor entnommenen Turbinenschaufeln können nach einer ggf. zeitintensiven Überholung wieder montiert werden. Alternativ dazu können andere, bereits anderweitig überholte Turbinenschaufeln oder Neuteile montiert werden, um die benötigte Wartungszeit für die Gasturbine möglichst kurz zu halten. Letzteres ist insbesondere bei Flugzeugtriebwerken von Bedeutung.Due to the particular load, the high-pressure turbine blades are regularly overhauled or, if this is not possible, replaced with new parts. For this purpose, the gas turbine must be dismantled at least to such an extent that the turbine blades of the high-pressure turbine can be removed. The previously removed turbine blades can be reassembled after a possibly time-consuming overhaul. Alternatively, other turbine blades or new parts that have already been otherwise overhauled can be installed in order to keep the required maintenance time for the gas turbine as short as possible. The latter is particularly important in aircraft engines.
Turbinenschaufeln verfügen regelmäßig über eine eindeutige Seriennummer. Für Turbinenschaufeln von Flugzeugtriebwerken ist dies aufgrund von Zulassungsbestimmungen sogar zwingend erforderlich. Die Seriennummern sind dabei an dem Fuß der Turbinenschaufeln, mit dem die Schaufeln am Schaufelträger des Triebwerks befestigt werden, angeordnet, um zu vermeiden, dass sie unmittelbar mit dem Heißgasstrom in Berührung kommen und durch diesen unkenntlich gemacht werden.Turbine blades regularly have a unique serial number. For turbine blades of aircraft engines is this is even mandatory due to approval regulations. The serial numbers are arranged on the base of the turbine blades, with which the blades are attached to the blade carrier of the engine, in order to avoid that they come into direct contact with the hot gas flow and are made unrecognizable by it.
Nachteilig an der Positionierung der Seriennummer am Fuß einer Turbinenschaufel ist, dass die Seriennummern nach dem Einsetzen der Turbinenschaufeln nicht mehr einsehbar sind. So ist es bei einer vollständig montierten Gasturbine bzw. einem vollständig montierten Flugzeugtriebwerk nicht möglich, die Seriennummer einer einzelnen Triebwerksschaufel zu überprüfen. Um die Seriennummer einer bestimmten Triebwerksschaufel zu ermitteln, ist gemäß dem Stand der Technik vielmehr ein nahezu vollständiges Zerlegen der gesamten Gasturbine erforderlich.The disadvantage of positioning the serial number at the base of a turbine blade is that the serial numbers can no longer be viewed after the turbine blades have been inserted. In the case of a completely assembled gas turbine or a completely assembled aircraft engine, for example, it is not possible to check the serial number of an individual engine blade. In order to determine the serial number of a specific engine blade, according to the prior art, it is rather necessary to almost completely dismantle the entire gas turbine.
Insbesondere bei der Verwendung von überholten Turbinenschaufeln kann sich selbst bei erfolgter Überprüfung der Turbinenschaufeln vor und während der Montage bereits kurz nach der Inbetriebnahme der wieder zusammengesetzten Gasturbine, teilweise bereits nach einem ersten Probelauf, ein zumindest leicht reduzierter Wirkungsgrad einstellen, der letztendlich einen erhöhten Treibstoffverbrauch im Einsatz der Gasturbine zur Folge hat. Auch wenn ein entsprechend reduzierter Wirkungsgrad häufig keine erneute Demontage der Gasturbine rechtfertigt, kann es aus verschiedenen Gründen erwünscht sein, dass den Wirkungsgradverlust hervorrufende Bauteil der Gasturbine eindeutig zu identifizieren. Beispielsweise ist eine entsprechende Identifikation wünschenswert, um evtl. Regressansprüche an den Hersteller eines eindeutig identifizierbaren Bauteils oder an den Wartungsbetrieb, der das fragliche Bauteil überholt hat, stellen zu können.Particularly when using overhauled turbine blades, even if the turbine blades have been checked before and during assembly, shortly after the reassembled gas turbine has been put into operation, in some cases already after a first test run, an at least slightly reduced degree of efficiency can occur, which ultimately results in increased fuel consumption Use of the gas turbine results. Even if a correspondingly reduced efficiency often does not justify a renewed dismantling of the gas turbine, it can be desirable for various reasons that the component of the gas turbine causing the loss of efficiency is clearly identified. For example, a corresponding identification is desirable in order to be able to make possible recourse claims against the manufacturer of a clearly identifiable component or against the maintenance company that overhauled the component in question.
Wird dabei eine Turbinenschaufel der Hochdruckturbine des Flugzeugtriebwerks als wahrscheinliche Ursache für den Wirkungsgradverlust ausgemacht, ist es im Stand der Technik allerdings nicht möglich, ohne eine nahezu vollständige Zerlegung der Gasturbine die fragliche Turbinenschaufel eindeutig, bspw. anhand ihrer Seriennummer, zu identifizieren. In der Folge lässt sich auch die Herkunft der Turbinenschaufel von einem Hersteller oder Reparaturbetrieb nicht ohne weiteres klären.If a turbine blade of the high-pressure turbine of the aircraft engine is identified as the probable cause of the loss of efficiency, however, in the prior art it is not possible to clearly identify the turbine blade in question, e.g. by means of its serial number, without an almost complete dismantling of the gas turbine. As a result, the origin of the turbine blade from a manufacturer or repair shop cannot be easily clarified.
Aus dem Stand der Technik - bspw. der
Die Dokumente
In der
Eine Aufgabe der vorliegenden Erfindung ist es, Verfahren zu schaffen, mit denen eine eindeutige Positionszuordnung und Identifizierung einer Turbinenschaufel einer Hochdruckturbinenstufe einer Gasturbine möglich ist, ohne das zur Identifizierung eine Demontage der Gasturbine erforderlich wäre. Gelöst wird diese Aufgabe durch Verfahren gemäß den Ansprüchen 1 und 5. Vorteilhafte Weiterbildungen sind Gegenstand der abhängigen Ansprüche.It is an object of the present invention to create methods with which an unambiguous position assignment and identification of a turbine blade of a high-pressure turbine stage of a gas turbine is possible without having to dismantle the gas turbine for identification. This object is achieved by the method according to
Demnach betrifft die Erfindung ein Verfahren zur eindeutigen Positionszuordnung einer Turbinenschaufel einer über eine Welle mit einem Hochdruckkompressor verbundenen Hochdruckturbinenstufe einer Gasturbine, wobei jede Turbinenschaufel der Hochdruckturbine eindeutig identifizierbar mit ihrer relativen Lage in einer Satzkarte verzeichnet wird, mit den Schritten:
- a. Ermitteln der Position eines vorgegebenen Schaufelschlosses einer vorgegebenen Stufe des Hockdruckkompressors, wobei die Stufe des Hockdruckkompressors derart gewählt ist, dass das Schaufelschloss im vollständig montierten Zustand der Gasturbine durch Drehen der Welle in das Sichtfeld eines durch eine erste Boroskopöffnung an der Gasturbine geführten ersten Boroskops bringbar und eindeutig identifizierbar ist; und
- b. Markierung derjenigen Turbinenschaufel auf der Satzkarte, die im vollständig montierten Zustand der Gasturbine im Sichtfeld eines durch eine zweite Boroskopöffnung an der Gasturbine geführten zweiten Boroskops ist, wenn das vorgegebene Schaufelschloss im Sichtfeld des ersten Boroskops ist.
- a. Determination of the position of a predetermined blade lock of a predetermined level of the high pressure compressor, the level of the high pressure compressor being selected such that the blade lock can be brought into the field of view of a first boroscope guided through a first boroscope opening on the gas turbine by rotating the shaft in the fully assembled state of the gas turbine is clearly identifiable; and
- b. Marking of the turbine blade on the record card that is in the fully assembled state of the gas turbine in the field of view of a second boroscope guided through a second borescope opening on the gas turbine when the specified blade lock is in the field of view of the first boroscope.
Weiterhin betrifft die Erfindung ein Verfahren zur eindeutigen Identifizierung der auf der Satzkarte mit dem vorstehenden erfindungsgemäßen Verfahren markierten Turbinenschaufel der Hochdruckturbine einer Gasturbine, mit den Schritten:
- a. Einführen eines ersten Boroskops durch eine erste Boroskopöffnung an der Gasturbine und eines zweiten Boroskops durch eine zweite Boroskopöffnung an der Gasturbine; und
- b. Drehen der den Hochdruckkompressor und die Hochdruckturbinenstufe verbindenden Welle, bis das vorgegebene Schaufelschloss im Sichtfeld des ersten Boroskops ist, womit die auf der Satzkarte markierte Turbinenschaufel im Sichtfeld des zweiten Boroskops ist.
- a. Inserting a first borescope through a first borescope opening on the gas turbine and a second borescope through a second borescope opening on the gas turbine; and
- b. Rotate the shaft connecting the high-pressure compressor and the high-pressure turbine stage until the specified blade lock is in the field of view of the first boroscope, so that the turbine blade marked on the set card is in the field of view of the second boroscope.
Zunächst werden einige im Rahmen der Erfindung verwendete Begriffe erläutert.First, some terms used in the context of the invention are explained.
Bei Gasturbinen bekannt und bei Flugzeugtriebwerken üblich sind "Satzkarten", auf denen die "relative Lage" der einzelnen Turbinen- oder Kompressorschaufeln einer Gasturbinenstufe verzeichnet sind. Auf der Satzkarte sind sämtliche in der Gasturbinenstufe eingesetzten Schaufeln anhand ihrer Seriennummer aufgelistet. Darüber hinaus geht aus der Satzkarte die Reihenfolge der einzelnen Schaufeln in Umfangsrichtung hervor. In anderen Worten lässt sich anhand der Satzkarte für jede Schaufel der Gasturbinenstufe ermitteln, welche beiden Schaufel jeweils benachbart dazu angeordnet sind. Die Satzkarte gibt dabei jedoch ausschließlich Auskunft über die relative Lage der Schaufeln, nicht jedoch die absolute Lage, bspw. gegenüber der Welle.Known in gas turbines and common in aircraft engines are "record cards" on which the "relative position" of the individual turbine or compressor blades of a gas turbine stage are recorded. All the blades used in the gas turbine stage are listed on the record card based on their serial number. In addition, the sequence of the individual blades in the circumferential direction emerges from the set card. In other words, the set map can be used to determine for each blade of the gas turbine stage which two blades are respectively arranged adjacent to it. However, the record card only provides information about the relative position of the blades, but not the absolute position, e.g. with respect to the shaft.
Schaufeln von Gasturbinen und Flugzeugtriebwerken umfassen ein Schaufelblatt und einen Schaufelfuß. Der Schaufelfuß weist dabei regelmäßig eine solche Formgebung auf, die ein Einschieben des Schaufelfußes in eine Schaufelnut des Schaufelträgers einer Turbinenstufe ermöglicht. Zur Sicherung einer oder mehrerer Schaufeln in der Schaufelnut sind ein oder mehrere "Schaufelschlösser" vorgesehen, mit denen die Schaufeln in ihrer Position gegenüber dem Schaufelträger fixiert werden.Gas turbine and aircraft engine blades include an airfoil and a root. The blade root regularly has a shape that enables the blade root to be pushed into a blade groove of the blade carrier of a turbine stage. To secure one or more blades in the blade groove, one or more "blade locks" are provided with which the blades are fixed in their position relative to the blade carrier.
Der Erfindung liegt die Erkenntnis zugrunde, dass die durch ein zweites Boroskop bei einer vollständig montierten Gasturbine einsehbaren Bereiche der Hochdruckturbine der besonderen Belastung durch das von der Brennkammer stammende Heißgas unterliegen, weshalb sämtliche in diesem Bereich angebrachte Markierungen spätestens mit einem ersten Probelauf der Gasturbine entfernt bzw. verbrannt werden würden. Aufgrund der besonderen Belastung in diesem Bereich sind die Hochdruckturbinen auch regelmäßig so ausgestaltet, dass die bei vollständig montierter Gasturbine durch ein zweites Boroskop einsehbaren Oberflächen der Hochdruckturbine keine Rückschlüsse auf deren Winkellage o.ä. zulassen.The invention is based on the knowledge that the areas of the high-pressure turbine that can be seen through a second borescope in a fully assembled gas turbine are subject to the particular load caused by the hot gas coming from the combustion chamber, which is why all markings made in this area are removed or removed at the latest with a first test run of the gas turbine would be burned. Due to the particular load in this area, the high-pressure turbines are also regularly designed in such a way that the surfaces of the high-pressure turbine, which can be viewed through a second borescope when the gas turbine is fully assembled, cannot draw any conclusions about their angular position or the like. allow.
Die Erfindung hat jedoch erkannt, dass der mit der Hockdruckturbine über eine Welle drehfest verbundene Hochdruckkompressor durch ein erstes Boroskop auch bei vollständig montierter Gasturbine eindeutig identifizierbare Schaufelschlösser aufweist, die als Erkennungsmerkmal für die Winkellage des Hochdruckkompressors und damit der Hochdruckturbine dienen können. Bei Kenntnis der Lage der Boroskopöffnungen für das erste und das zweite Boroskop lässt sich genau feststellen, welche Turbinenschaufel im Sichtfeld des zweiten Boroskops ist, wenn das vorgegebene Schaufelschloss im Sichtfeld des ersten Boroskops ist.However, the invention has recognized that the high-pressure compressor, which is non-rotatably connected to the high-pressure turbine via a shaft, has clearly identifiable vane locks through a first borescope, even when the gas turbine is fully installed, which can serve as an identification feature for the angular position of the high-pressure compressor and thus the high-pressure turbine. With knowledge of the position of the borescope openings for the first and second borescopes, it is possible to determine precisely which turbine blade is in the field of view of the second boroscope when the specified blade lock is in the field of view of the first boroscope.
Indem dieser Zusammenhang erfindungsgemäß während der Montage der Hochdruckturbine auf der Satzkarte verzeichnet wird, kann anhand dieser Information auf der Satzkarte bei vollständig montierter Gasturbine zunächst eine erste Turbinenschaufel eindeutig identifiziert werden. Durch anschließendes Drehen des Hochdruckkompressors um einen vorgegebenen Winkel oder bei gleichzeitiger Beobachtung durch das zweite Boroskop können anhand der auf der Satzkarte verzeichneten relativen Lage der Turbinenschaufeln auch die übrigen Turbinenschaufeln eindeutig identifiziert werden.Since this relationship is recorded according to the invention on the record card during the assembly of the high-pressure turbine, a first turbine blade can initially be clearly identified on the basis of this information on the record card when the gas turbine is fully assembled. By subsequently rotating the high-pressure compressor by a predetermined angle or by simultaneous observation through the second borescope, the other turbine blades can also be clearly identified using the relative position of the turbine blades recorded on the record map.
Um die Ermittlung der auf der Satzkarte zu markierenden Turbinenschaufel zu erleichtern, ist es bevorzugt, wenn zunächst die Winkellage des vorgegebenen Schaufellschlosses des Hochdruckkompressors gegenüber der Welle auf der Welle selbst markiert wird und ausgehend von dieser Markierung die auf der Satzkarte zu markierende Turbinenschaufel ermittelt wird. Die Markierung kann dabei entlang der Welle bis an die Hochdruckturbine herangeführt werden, wodurch das Identifizieren der fraglichen Turbinenschaufel vereinfacht wird. Die Markierung kann bspw. durch einen Markierungsstift entsprechend der Norm DIN LN 9051 erfolgen.In order to facilitate the determination of the turbine blade to be marked on the record card, it is preferred if the angular position of the specified blade lock of the high pressure compressor relative to the shaft is marked on the shaft itself and, based on this marking, the turbine blade to be marked on the record card is determined. The marking can be brought up to the high pressure turbine along the shaft, which simplifies the identification of the turbine blade in question. The marking can be carried out, for example, using a marking pen in accordance with the DIN LN 9051 standard.
Die Ermittlung der auf der Satzkarte zu markierenden Turbinenschaufel kann alternativ oder zusätzlich erleichtert werden, wenn die Turbinenschaufeln ein nach der Montage sichtbares temporäres Identifikationsmerkmal aufweisen. So kann z.B. die Seriennummer der einzelnen Turbinenschaufeln unmittelbar auf dem Schaufelblatt aufgebracht sein, also an einer Stelle, die auch nach dem Einbau der Turbinenschaufel sichtbar ist. Bei einem solchen auch im eingebauten Zustand sichtbaren Identifikationsmerkmal handelt es sich grundsätzlich um ein temporäres Identifikationsmerkmal, welche nach einem ersten Testlauf der Gasturbine aufgrund der besonderen Belastungen im Bereich der Hochdruckturbine bereits rückstandslos verbrannt sind.The determination of the turbine blades to be marked on the record card can alternatively or additionally be made easier if the turbine blades have a temporary identification feature that is visible after assembly. E.g. the serial number of the individual turbine blades must be applied directly to the blade, i.e. at a point that is also visible after the turbine blade has been installed. Such an identification feature, which is also visible in the installed state, is basically a temporary identification feature which, after a first test run of the gas turbine, has already been burned without residue due to the particular loads in the area of the high-pressure turbine.
Sind mehr als zwei Schaufelschlösser in der vorgegebenen Stufe des Hockdruckkompressors vorhanden, lässt sich im Regelfall eindeutig ein erstes und ein zweites Schaufelschloss identifizieren. Der Abstand in Umfangsrichtung entgegen einer vorgegebenen Drehrichtung zwischen dem ersten Schaufelschloss und dem zweiten Schaufelschloss ist im Regelfall nämlich geringer als der entsprechende Abstand zwischen dem letzten Schaufelschloss - das auch das zweite Schaufelschloss sein kann - und dem ersten Schaufelschloss. Ausgehend von dem so eindeutig identifizierbaren ersten Schaufelschloss ist das zweite Schaufelschloss das in der vorgegebenen Drehrichtung in Umfangsrichtung dem ersten Schaufelschloss nachfolgende Schaufelschloss. Es ist bevorzugt, wenn das vorgegebene Schaufelschloss das zweite Schaufelschloss ist. Wie nachfolgend erläutert, kann dadurch die spätere Identifizierung der auf der Satzkarte markierten Turbine erleichtert werden.If there are more than two vane locks in the specified stage of the high-pressure compressor, a first and a second vane lock can usually be clearly identified. The distance in the circumferential direction opposite to a predetermined direction of rotation between the first shovel lock and the second shovel lock is usually less than the corresponding distance between the last shovel lock - which can also be the second shovel lock - and the first Shovel lock. Proceeding from the first shovel lock, which can be clearly identified in this way, the second shovel lock is the shovel lock following the first shovel lock in the specified direction of rotation in the circumferential direction. It is preferred if the specified shovel lock is the second shovel lock. As explained below, this can facilitate the later identification of the turbine marked on the record card.
Ist eine Turbinenschaufel erfindungsgemäß auf der Satzkarte markiert, lässt sich diese Turbinenschaufel auch bei vollständig montierter Gasturbine eindeutig identifizieren.If a turbine blade is marked according to the invention on the record card, this turbine blade can be clearly identified even when the gas turbine is fully assembled.
Dazu werden ein erstes Boroskop durch eine erste Boroskopöffnung an der Gasturbine und ein zweites Boroskop durch eine zweite Boroskopöffnung an der Gasturbine geführt. Die erste Boroskopöffnung ist dabei so angeordnet, dass durch ein hindurchgeführtes Boroskop das vorgegebene Schaufelschloss der vorgegebenen Stufe des Hochdruckkompressors eingesehen werden kann, während die zweite Boroskopöffnung eine Betrachtung der Turbinenschaufeln der relevanten Hochdruckturbinenstufe mit Hilfe eines Boroskops gestattet.For this purpose, a first borescope is guided through a first borescope opening on the gas turbine and a second borescope is guided through a second borescope opening on the gas turbine. The first borescope opening is arranged so that the given blade lock of the given stage of the high pressure compressor can be seen through a passed borescope, while the second borescope opening allows the turbine blades of the relevant high pressure turbine stage to be viewed with the aid of a boroscope.
Nach Einführung zumindest des ersten Boroskops - das zweite Boroskop kann auch noch später eingeführt werden - wird die Welle auf die sowohl der Hochdruckkompressor als auch die Hochdruckturbinenstufe gedreht, bis das vorgegebene Schaufelschloss im Sichtfeld des ersten Boroskops ist. Die Turbinenschaufel, die dann durch das spätestens jetzt eingeführte zweite Boroskop sichtbar ist, ist dann die auf der Satzkarte markierte Turbinenschaufel.After introducing at least the first boroscope - the second borescope can also be inserted later - the shaft is turned on both the high pressure compressor and the high pressure turbine stage until the specified blade lock is in the field of view of the first boroscope. The turbine blade, which is then visible through the second borescope, which has now been introduced at the latest, is then the turbine blade marked on the record card.
Handelt es sich bei dem vorgegebenen Schaufelschloss um das zweite Schaufelschloss der vorgegebenen Stufe des Hochdrucckompressors, kann die Drehgeschwindigkeit nach Erkennen des ersten Schaufelschlosses durch das erste Boroskop vorzugsweise reduziert werden, um die Welle möglichst verzögerungsfrei anhalten zu können, sobald das zweite Schaufelschlosses im Sichtfeld des ersten Boroskops ist. In anderen Worten kann die Drehgeschwindigkeit zunächst vergleichsweise hoch sein, um die Welle zügig in den Bereich zu drehen, in dem das zweite Schaufelschloss liegt, um dann aufgrund einer vergleichsweise niedrigen Drehgeschwindigkeit die Welle unmittelbar anhalten zu können, sobald das zweite Schaufelschloss ins Sichtfeld des ersten Boroskops kommt.If the specified vane lock is the second vane lock of the specified stage of the high-pressure compressor, the rotational speed can be determined after the first shovel lock can preferably be reduced by the first borescope in order to be able to stop the wave without delay as soon as the second shovel lock is in the field of view of the first borescope. In other words, the rotational speed can initially be comparatively high in order to quickly turn the shaft into the area in which the second shovel lock is located, in order then to be able to stop the shaft immediately due to a comparatively low rotational speed as soon as the second shovel lock is in the field of vision of the first Boroscope is coming.
Ist die auf der Satzkarte markierte Turbinenschaufel eindeutig identifiziert, können vorzugsweise durch anschließendes Drehen der den Hochdruckkompressor und die Hochdruckturbinenstufe verbindenden Welle unter Beobachtung der Turbinenschaufeln durch das zweite Boroskop oder unter Beobachtung der Veränderung der Winkellage der Welle wenigstens eine Turbinenschaufel anhand der Satzkarte identifiziert wird. Da auf der Satzkarte die relative Lage der einzelnen Turbinenschaufeln hervorgeht können ausgehend von der eindeutig identifizierten markierten Turbinenschaufel die jeweils benachbarten Turbinenschaufeln und nacheinander die daran anschließenden Turbinenschaufeln identifiziert werden. Da die grundsätzliche geometrische Konfiguration der Turbinenschaufeln einer Gasturbine bekannt ist, kann auch über die Winkellage der Welle ausgehend von der Winkellage, die die Welle bei der Identifizierung der markierten Turbinenschaufel einnimmt, unmittelbar auch eine nicht zur markierten Turbinenschaufel benachbarte Turbinenschaufel identifiziert werden.If the turbine blade marked on the rate card is clearly identified, at least one turbine blade can be identified on the basis of the rate card, preferably by subsequently turning the shaft connecting the high pressure compressor and the high pressure turbine stage while observing the turbine blades through the second borescope or while observing the change in the angular position of the shaft. Since the relative position of the individual turbine blades can be seen on the record card, starting from the clearly identified, marked turbine blade, the respective adjacent turbine blades and successively the adjacent turbine blades can be identified. Since the basic geometric configuration of the turbine blades of a gas turbine is known, a turbine blade that is not adjacent to the highlighted turbine blade can also be identified directly via the angular position of the shaft, starting from the angular position that the shaft assumes when the marked turbine blade is identified.
Die Erfindung wird nun anhand eines Ausführungsbeispiels unter Bezugnahme auf die beigefügten Zeichnungen beispielhaft beschrieben. Es zeigen:
- Figur 1:
- eine Hochdruckturbinenstufe mit einem über eine Welle verbundenen Hochdruckkompressor;
- Figur 2:
- eine Detaildarstellung des Hochdruckkompressors aus
Figur 1 ; und - Figur 3:
- ein Flugzeugtriebwerk mit der Hochdruckturbinenstufe und dem Hochdruckkompressor gemäß
Figur 1 .
- Figure 1:
- a high pressure turbine stage with a high pressure compressor connected by a shaft;
- Figure 2:
- a detailed representation of the high pressure compressor
Figure 1 ; and - Figure 3:
- an aircraft engine with the high pressure turbine stage and the high pressure compressor according to FIG
Figure 1 .
Die Hochdruckturbinenstufe 10 ist über eine Welle 20 drehfest mit einem zweistufigen Hochdruckkompressor 30 verbunden. Jede der beiden Stufen des Hochdruckkompressors 30 umfasst eine Vielzahl von Kompressorschaufeln 31, die über jeweils zwei Schaufelschlösser 32 (in der Darstellung gemäß
In
Das so als zweites Schaufelschloss 32 identifizierte Schaufelschloss 32 dient als Basis für die Markierung 21 entlang der Welle 20, die mit einem luftfahrtzertifizierten Markierungsstift aufgebracht wird. Die Markierung 21 zeigt dabei die Winkellage des Schaufelschlosses 32 gegenüber der Achse der Welle 20 an. Ausgehend von dieser Markierung kann diejenige Turbinenschaufel 11' auf der Satzkarte markiert werden, die - wie nachfolgend anhand von
In
Zu eindeutigen Identifizierung der auf der Satzkarte markierten Turbinenschaufel 11' der Hochdruckturbine 10 wird die Welle 20 mit einer ersten Drehgeschwindigkeit in die Drehrichtung 90 gedreht. Sobald durch das erste Boroskop 41 das erste Schaufelschloss 32' zu erkennen ist, wird die Drehgeschwindigkeit reduziert und die Welle 20 wird, sobald das zweite Schaufelschloss 32 im Blickfeld des ersten Boroskops 41 ist gestoppt.For unambiguous identification of the
Ist das zweite Schaufelschloss 32 im Blickfeld des ersten Boroskops 41 befindet sich, aufgrund der zuvor erfolgten Positionszuordnung der fraglichen Turbinenschaufel 11 die auf der Satzkarte markierte Turbinenschaufel 11 unmittelbar im Sichtfeld des zweiten Boroskops 42. Die übrigen Turbinenschaufeln 11 können dann ausgehend von der markierten Turbinenschaufel 11' anhand der Satzkarte eindeutig identifiziert werden.If the
Während der Montage ggf. vorgesehene Markierungen auf den Turbinenschaufeln 11, die auch die Positionszuordnung der zu markierenden Turbinenschaufel 11' erleichtern können, sind spätestens nach dem ersten Testlauf des Flugzeugtriebwerks 1 vollständig entfernt. Durch die erfindungsgemäßen Verfahren ist es aber möglich, zunächst eine - nämlich die zuvor auf der Satzkarte markierte - Turbinenschaufel 11' ohne jegliche Identifikationsmerkmale an der Turbinenschaufel 11' oder der Hochdruckturbine 10 selbst, zu identifizieren. Ausgehend von dieser Turbinenschaufel 11' können mithilfe der Satzkarte auch die übrigen Turbinenschaufeln 11 eindeutig identifiziert werden. Any markings provided on the
Claims (7)
- Method for the clear position determination of a turbine blade (11) of a high-pressure turbine stage (10) of a gas turbine (1) that is connected to a high-pressure compressor (30) via a shaft (20), wherein each turbine blade (11) of the high-pressure turbine (10) is recorded on a record card in a clearly identifiable manner with the relative position thereof, comprising the steps:a. determining the position of a predefined blade lock (32) of a predefined stage of the high-pressure compressor (30), wherein the stage of the high-pressure compressor (30) is selected such that, in the completely mounted state of the gas turbine (1), the blade lock (32) can be brought into the field of view of a first boroscope (41) guided through a first boroscope opening (4) on the gas turbine (1) by rotating the shaft (20) and be identified clearly; andb. marking that turbine blade (11') on the record card which, in the completely mounted state of the gas turbine (1), is in the field of view of a second boroscope (42) guided through a second boroscope opening (5) on the gas turbine (1) when the predefined blade lock (32) is in the field of view of the first boroscope (41).
- Method according to Claim 1,
characterized in that
when there is more than one blade lock (32, 32') in a predefined stage of the high-pressure compressor (30), the second blade lock (32) is the predefined blade lock, wherein the distance between the first blade lock (32') and the second blade lock (32) in the circumferential direction counter to a predefined direction of rotation (90) is smaller than the distance between the second blade lock (32) and the first blade lock (32') in the circumferential direction counter to a predefined direction of rotation (90) . - Method according to one of the preceding claims,
characterized in that
the angular position of the predefined blade lock (32) relative to the shaft (20) is marked on the shaft (20) and, starting from this marking (21), turbine blade (11') to be marked on the record card is determined. - Method according to one of the preceding claims,
characterized in that
the turbine blades (11) have an identification feature which is visible following the mounting in the high-pressure turbine stage (10) and which is removed by the operation of the gas turbine (1). - Method for the clear identification of the turbine blade (11') of the high-pressure turbine (10) of a gas turbine (1) which is marked on the record card by a method according to the preceding claims, comprising the steps:a. inserting a first boroscope (41) through a first boroscope opening (4) on the gas turbine (1) and a second boroscope (5) through a second boroscope opening (42) on the gas turbine (1); andb. rotating the shaft (20) connecting the high-pressure compressor (30) and the high-pressure turbine stage (10) until the predefined blade lock (32) is in the field of view of the first boroscope (41), whereby the turbine blade (11') marked on the record card is in the field of view of the second boroscope (42).
- Method according to Claim 5,
characterized in that
with a second blade lock (32) as a predefined blade lock, the rotational speed is reduced following detection of the first blade lock (32') through the first boroscope (41) in order to stop the shaft without delay when the second blade lock (32) is in the field of view of the first boroscope (41). - Method according to Claim 5 or 6,
characterized in that
following clear identification of the turbine blades (11') marked on the record card, by means of subsequent rotation of the shaft (20) connecting the high-pressure compressor (30) and the high-pressure turbine stage (10) while observing the turbine blades (11) through the second boroscope (42) and/or while observing the change in the angular position of the shaft (20), at least one further turbine blade (11) is identified by using the record card.
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DE102016216895.9A DE102016216895B4 (en) | 2016-09-06 | 2016-09-06 | Method for unique position assignment and identification of a turbine blade |
PCT/EP2017/072052 WO2018046423A1 (en) | 2016-09-06 | 2017-09-04 | Method for clear position determination and identification of a turbine blade |
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